[Federal Register: August 28, 2007 (Volume 72, Number 166)]
[Rules and Regulations]
[Page 49177-49180]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28au07-17]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26771; Directorate Identifier 2005-SW-07-AD;
Amendment 39-15059; AD 2007-11-02]
RIN 2120-AA64
Airworthiness Directives; Enstrom Helicopter Corporation Model F-
28A, F-28C, F-28F, TH-28, 280, 280C, 280F, 280FX, 480, and 480B
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Enstrom Helicopter Corporation (Enstrom) Model F-28A, F-28C, F-28F, TH-
28, 280, 280C, 280F, 280FX, 480, and 480B helicopters that requires
determining the installation dates for each main rotor push-pull
control rod (push-pull rod), inspecting the push-pull rods for
corrosion, replacing any push-pull rod which has corrosion that is
severe enough to cause pitting, or has visible moisture inside the rod,
and repairing each push-pull rod that has corrosion but no pitting.
This amendment is prompted by one reported incident in which the
helicopter pilot encountered severe in-flight vibration due to the
failure of a push-pull rod, requiring an emergency landing. The actions
specified by this AD are intended to detect corrosion and prevent
failure of a push-pull rod, and subsequent loss of control of the
helicopter.
DATES: Effective October 2, 2007.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 2, 2007.
ADDRESSES: You may get the service information identified in this AD
from The Enstrom Helicopter Corporation, Twin County Airport, P.O. Box
490, Menominee, Michigan 49858.
[[Page 49178]]
Examining the Docket
You may examine the docket that contains this AD, any comments, and
other information on the Internet at http://dms.dot.gov or at the
Docket Operations office, West Building Ground Floor, Room W12-140,
1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Shawn Malekpour, Aviation Safety
Engineer, FAA, Chicago Aircraft Certification Office, 2300 East Devon
Ave., Des Plaines, Illinois 60018, telephone (847) 294-7837, fax (847)
294-7834.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for the specified model helicopters was published in the
Federal Register on January 8, 2007 (72 FR 669). That action proposed
to require reviewing the helicopter maintenance records and determining
the installation dates for the push-pull rods. If the dates cannot be
determined from the maintenance records, using the ``Date MFD'', which
is located on the helicopter data plate, was proposed to be used as the
installation date for the push-pull rods. That action also proposed to
require a visual inspection for corrosion on the exterior and interior
of the three push-pull rods, part number (P/N) 28-16253-all dash
numbers (for Model F-28A, F-28C, F-28F, 280, 280C, 280F, and 280FX
helicopters) or P/N 4140532-all dash numbers (for Model TH-28, 480, and
480B helicopters), using the compliance times stated in the following
table. Replacing any push-pull rod that has corrosion that is severe
enough to cause pitting or has moisture inside the rod, and repairing
any push-pull rod that has corrosion but no pitting, was proposed to be
required before further flight. Repairing a push-pull rod consists of
cleaning the push-pull rod, applying a protective coating, and sealing
the push-pull rod before remarking and reinstalling it on a helicopter.
------------------------------------------------------------------------
Push-pull rod
Helicopter models service life Compliance times
------------------------------------------------------------------------
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 10
280, 280C, 280F, and 280FX has been installed hours time-in-
helicopters. for 20 or more service (TIS) or at
years. next annual
inspection,
whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 50
280, 280C, 280F, and 280FX has been installed hours TIS or at the
helicopters. for 10 or more next annual
years, but less inspection,
than 20 years. whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect before the
280, 280C, 280F, and 280FX has been installed service life of the
helicopters. for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
Model TH-28, 480, and 480B Push-pull rod that Inspect within 50
helicopters. has been installed hours TIS or at the
for 10 or more next annual
years. inspection,
whichever occurs
first.
Model TH-28, 480, and 480B Push-pull rod that Inspect before the
helicopters. has been installed service life of the
for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
------------------------------------------------------------------------
We have reviewed the following service information:
Enstrom Helicopter Corporation Service Directive Bulletin
No. 0096, dated September 10, 2003, which describes visually inspecting
the push-pull rods for corrosion and internal moisture, provides for
repairing light corrosion, and is applicable to Model F-28A, F-28C, F-
28F, 280, 280C, 280F, and 280FX helicopters.
Enstrom Helicopter Corporation Service Directive Bulletin
No. T-019, dated September 10, 2003, which describes visually
inspecting the push-pull rods for corrosion and internal moisture,
provides for repairing light corrosion, and is applicable to Model TH-
28, 480, and 480B helicopters.
Enstrom Helicopter Corporation Service Information Letter
(SIL) No. T-019, dated December 9, 2003, applicable to Model TH-28,
480, and 480B helicopters, which describes visually inspecting each
push-pull rod for a crack, nick, scratch, dent, corrosion, damaged
threads, bending, and contact wear. We are not proposing to require the
inspections specified in the SIL.
Enstrom Helicopter Corporation Service Information Letter
No. 0156, dated December 9, 2003, applicable to Model F-28A, F-28C, F-
28F, 280, 280C, 280F, and 280FX helicopters, which describes visually
inspecting each push-pull rod for a crack, nick, scratch, dent,
corrosion, damaged threads, bending, and contact wear. We are not
proposing to require the inspections specified in the SIL.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
The FAA estimates that this AD will affect 378 helicopters of U.S.
registry, and the required actions will take the following numbers of
work hours to accomplish on each helicopter at an average labor rate of
$80 per work hour:
8 work hours to remove, disassemble, and inspect the 3
push-pull rods;
9 work hours to repair corrosion without pitting, remark
each push-pull rod, and reassemble each push-pull rod; and
3 work hours to reinstall 3 push-pull rods on the
helicopter.
Required parts will cost approximately $900 per helicopter. Based on
these figures, the total cost impact of the AD on U.S. operators will
be $945,000 ($2,500 per helicopter), assuming 3 push-pull rods are
replaced on each helicopter.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD. See the DMS to examine the economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 49179]]
rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2007-11-02 Enstrom Helicopter Company: Amendment 39-15059. Docket
No. FAA-2006-26771; Directorate Identifier 2005-SW-07-AD.
Applicability: Model F-28A, F-28C, and F-28F helicopters,
excluding serial number (S/N) 816 and subsequent; Model 280, 280C,
280F, and 280FX helicopters, excluding S/N 2100 and subsequent; and
Model TH-28, 480, and 480B helicopters, excluding S/N 5058 and
subsequent, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect corrosion and prevent failure of a main rotor push-
pull control rod (push-pull rod), and subsequent loss of control of
the helicopter, accomplish the following:
(a) Within 10 hours time-in-service (TIS) or at the next annual
inspection, whichever occurs first, review the helicopter
maintenance records and determine the date that each push-pull rod,
part number (P/N) 28-16253--all dash numbers (for Model F-28A, F-
28C, F-28F, 280, 280C, 280F, and 280FX helicopters) and P/N
4140532--all dash numbers (for Model TH-28, 480, and 480B
helicopters), was installed. If the date cannot be determined from
the maintenance records, use the ``Date MFD'', which is located on
the helicopter data plate, as the installation date for the push-
pull rod.
(b) For Model F-28A, F-28C, F-28F, 280, 280C, 280F, and 280FX
helicopters, using the compliance times stated in Table 1 of this
AD, visually inspect the exterior and interior of each of the three
push-pull rods for corrosion severe enough to cause pitting or any
moisture, paying special attention to the area of the lower fitting,
in accordance with section 5.1., INSPECTION, in Enstrom Helicopter
Corporation Service Directive Bulletin No. 0096, dated September 10,
2003 (SDB 0096).
Table 1
------------------------------------------------------------------------
Push-pull rod
Helicopter models service life Compliance times
------------------------------------------------------------------------
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 10
280, 280C, 280F, and 280FX has been installed hours time-in-
helicopters. for 20 or more service (TIS) or at
years. next annual
inspection,
whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect within 50
280, 280C, 280F, and 280FX has been installed hours TIS or at the
helicopters. for 10 or more next annual
years, but less inspection,
than 20 years. whichever occurs
first.
Model F-28A, F-28C, F-28F, Push-pull rod that Inspect before the
280, 280C, 280F, and 280FX has been installed service life of the
helicopters. for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
------------------------------------------------------------------------
(1) Before further flight, if corrosion without pitting is found
on a push-pull rod, then repair, reassemble, remark, and reinstall
it in accordance with section 5.2., REPAIR/REASSEMBLY, in SDB 0096.
(2) Before further flight, if corrosion is found that is severe
enough to cause pitting, or if any moisture is visible on the inside
of a push-pull rod, replace it with an airworthy push-pull rod.
Note 1: Determining continued serviceability of the push-pull
rods by inspecting the exterior only of each push-pull rod is
described in Enstrom Helicopter Corporation Service Information
Letter No. 0156, dated December 9, 2003.
(c) For Model TH-28, 480 and 480B helicopters, using the
compliance times stated in Table 2 of this AD, visually inspect the
exterior and interior of each of the three push-pull rods for
corrosion severe enough to cause pitting or any moisture, paying
special attention to the area of the lower fitting, in accordance
with section 5.1., INSPECTION, in Enstrom Helicopter Corporation
Service Directive Bulletin No. T-019, dated September 10, 2003 (SDB
T-019).
Table 2
------------------------------------------------------------------------
Push-pull rod
Helicopter models service life Compliance times
------------------------------------------------------------------------
Model TH-28, 480, and 480B Push-pull rod that Inspect within 50
helicopters. has been installed hours TIS or at the
for 10 or more next annual
years. inspection,
whichever occurs
first.
Model TH-28, 480, and 480B Push-pull rod that Inspect before the
helicopters. has been installed service life of the
for less than 10 push-pull rod
years. reaches 10 years
since initial
installation.
------------------------------------------------------------------------
(1) Before further flight, if corrosion without pitting is found
on a push-pull rod, then repair, reassemble, remark, and reinstall
it in accordance with section 5.2., REPAIR/REASSEMBLY, in SDB T-019.
(2) Before further flight, if corrosion is found that is severe
enough to cause pitting, or if any moisture is visible on the inside
of a push-pull rod, replace it with an airworthy push-pull rod.
Note 2: Determining continued serviceability of the push-pull
rods by inspecting the exterior only of each push-pull rod is
described in Enstrom Helicopter
[[Page 49180]]
Corporation Service Information Letter No. T-019, dated December 9,
2003.
(d) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Chicago Aircraft Certification Office, Small Airplane
Directorate, FAA, for information about previously approved
alternative methods of compliance.
(e) The inspection and replacement, if necessary, shall be done
in accordance with Enstrom Helicopter Corporation Service Directive
Bulletin No. 0096, dated September 10, 2003; Enstrom Helicopter
Corporation Service Directive Bulletin No. T-019, dated September
10, 2003; Enstrom Helicopter Corporation Service Information Letter
No. T-019, dated December 9, 2003; or Enstrom Helicopter Corporation
Service Information Letter No. 0156, dated December 9, 2003, as
applicable. The Director of the Federal Register approved these
incorporations by reference in accordance with 5 U.S.C. 552(a) and 1
CFR part 51. Copies may be obtained from The Enstrom Helicopter
Corporation, Twin County Airport, P.O. Box 490, Menominee, Michigan
49858. Copies may be inspected at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas or at the National Archives and Records Administration (NARA).
For information on the availability of this material at NARA, call
202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
(f) This amendment becomes effective on October 2, 2007.
Issued in Fort Worth, Texas, on July 5, 2007.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-16770 Filed 8-27-07; 8:45 am]
BILLING CODE 4910-13-P